US4369937A - Hinging and latching apparatus - Google Patents
Hinging and latching apparatus Download PDFInfo
- Publication number
- US4369937A US4369937A US06/264,268 US26426881A US4369937A US 4369937 A US4369937 A US 4369937A US 26426881 A US26426881 A US 26426881A US 4369937 A US4369937 A US 4369937A
- Authority
- US
- United States
- Prior art keywords
- guide hole
- suppressor
- effective
- alignment
- guide pin
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired - Fee Related
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Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
- B64D33/04—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of exhaust outlets or jet pipes
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T292/00—Closure fasteners
- Y10T292/08—Bolts
- Y10T292/0911—Hooked end
- Y10T292/0913—Sliding and swinging
- Y10T292/0914—Operating means
- Y10T292/0917—Lever
Definitions
- the present invention relates to hinging and latching mechanism and, more particularly, to hinging and latching mechanisms for supporting and securing an infrared suppressor to the aft end of a gas turbine engine.
- Infrared suppression devices have been developed which permit the exhaust gases from the gas turbine engine to expand considerably before being vented to the atmosphere. This tends to reduce the exhaust gas temperature and to reduce the temperature of material near the exhaust opening. Furthermore, the exhaust opening itself can be redirected to locations which make it less vulnerable to hostile fire. For example, it is particularly desirable to relocate the gas turbine engine exhaust from its previous position directly aft. In this undesirable aft position, an excellent relatively angularly stationary target for portable infrared-seeking weapons was presented. Side-discharge and top-discharge infrared suppressors have improved the situation considerably. In addition, some infrared suppressors provide an auxiliary air intake which permits the mixing of cooler ambient air into the turbine engine exhaust prior to discharging the exhaust into the atmosphere. This further reduces the infrared signature but increases the bulk of the apparatus considerably.
- the apparatus further includes means for guiding the forward end of the infrared suppressor in the fore-and-aft directions to align latching element before the final latching operation is performed.
- an apparatus for mounting an infrared suppressor to an aircraft and for mating a first end of the infrared suppressor to a second end of an engine comprising hinge means for attaching the infrared suppressor to the aircraft, the hinge means including means for supporting and permitting the infrared suppressor to be rotated on an axis away from the second end whereby the second end is made accessible, the hinge means further including means permitting the first end to be rotated into alignment with the second end and further permitting generally linear translation of the infrared suppressor into mating engagement of the first end with the second end, and means for maintaining a predetermined minimum spacing of the first end from the second end during rotation of the infrared suppressor into alignment.
- an apparatus for mounting an infrared suppressor to an aircraft and for mating a first end of the infrared suppressor to a second end of an engine comprising first and second spaced apart straps, a synchronizing bar rigidly joining the straps, the first and second straps each having a first pivot at a first end thereof affixed at a first axis to the aircraft, axes of the first pivots being aligned, the first and second straps each having a second pivot at a second end thereof affixed to the infrared suppressor, axes of the second pivots being aligned, the infrared suppressor being rotatable about axes of the second pivots and being generally linearly displaceable by rotation of the first and second straps about axes of the first pivots, rotation about axes of the second pivots permitting the infrared suppressor to be rotated away from the second end whereby the second end is made accessible, and permitting the first end
- FIG. 1 is a top view of a portion of a helicopter including a hinging and latching mechanism according to an embodiment of the present invention.
- FIG. 2 is a partial view of the side of a helicopter showing a two-point hinge suitable for use in the present invention from which the infrared suppressor has been omitted to reveal details of the two-point hinge.
- FIG. 3 shows a perspective view of the aft end of a gas turbine engine and the forward end of an infrared suppressor and shows a guided trajectory of parts attached to the infrared suppressor during alignment of the infrared suppressor with the aft end of the gas turbine engine.
- FIG. 4 is a cross sectional close-up view of a portion of the latch mechanism shown aligned but before latching.
- FIG. 5 is a view similar to FIG. 4 in which latching has been completed.
- FIG. 1 there is shown a partial overhead view of a helicopter 10, having a body 12 to which are affixed left and right gas turbine engines 14 and 16.
- IR suppressor assemblies 18 and 20 are mated with aft ends 22 and 24 of left and right gas turbine engines 14 and 16, respectively.
- IR suppressors 18 and 20 are arranged to move backward and swing away from aft ends 22 and 24 in the manner illustrated for IR suppressor 20.
- the backward movement and rotation of IR suppressor 20 is permitted by a two-point hinge shown generally at 26.
- Two-point hinge 26 includes a strap 28 pivoted to body 12 at a first pivot 30 and pivoted to IR suppressor 20 at a second pivot 32. This arrangement permits second pivot 32 to be moved backward and forward as indicated by a double-headed arrow 34.
- top and bottom mounting flanges 36 and 36' affixed to body 12 provide means for pivoting top and bottom straps 28 and 28' at corresponding pivots 30 and 30'.
- a synchronizing bar 38 is rigidly affixed between top and bottom straps 28 and 28' to ensure that rotation of upper strap 28 indicated by double-headed arrow 34 is synchronized with, and equal to motion of lower strap 28' indicated by double-headed arrow 34'.
- aft end 24 or firewall of left gas turbine engine 14 includes a pair of loops 40 and 42 which are respectively engaged by corresponding hooks 44 and 46 of a latching apparatus to be more fully described hereinafter.
- an apparatus is provided for guiding a forward end 48 of IR suppressor 20 during reassembly and fastening of IR suppressor 20 to aft end 24.
- Part of such guiding apparatus includes a roller 50 on IR suppressor 20 and a track 52 across the exposed aft end 22 of left turbine engine 14.
- roller 50 If IR suppressor 20 is swung into alignment with left gas turbine engine 14 while two-point hinge 26 is in its forward position, roller 50 describes a trajectory shown by a dashed line 54 wherein it follows a curving pass until makes contact with track 52 at a contact point 56 and then follows a straight pass along track 52 thereby establishing and maintaining the proper spacing between forward end 48 and aft end 24 while IR suppressor 20 is rotated into a position wherein hooks 44 and 46 are aligned for engagement with loops 40 and 42, respectively.
- hooks 44 and 46 are retracted after engagement with loops 40 and 42 to pull IR suppressor 20 forward a substantial amount such as, for example, about 1.5 inches and thereby to compress a resilient sealing material to seal the junction against loss of gas.
- a well 58 is provided beyond the end of track 52.
- IR suppressors 18 and 20 are identical except for handedness, only the attachment and operation of IR suppressor 20 is described in detail.
- IR suppressor 20 is further seen to include first and second guide pins 60 and 62 which preferably have ogive-shaped forward ends projecting forward from forward end 48. Although other arrangements are possible, guide pins 60 and 62 are seen to be generally respectively aligned with hooks 44 and 46.
- First and second guide holes 64 and 66 are provided in aft end 24 for respective engagement by guide pins 60 and 62 during the final stages of latching IR suppressor 20 in place.
- Pin 62 for example, follows a trajectory shown by dashed line 68 on a curving line until roller 50 contacts at 52 and is then maintained spaced from aft end 24 an appropriate distance while it is translated laterally into alignment with guide hole 66.
- a flange 70 supports guide pin 62 in the last few inches of its transition.
- a positioning groove 72 functions as a detent engaged by guide pin 62 to indicate that guide pin 62 is centered in front of guide hole 66.
- FIGS. 4 and 5 a latching mechanism is shown in greater detail. Although certain lever and camming elements for actuating the parts shown are required, such mechanisms are conventional and their description in full would merely impede understanding of the present invention.
- FIG. 4 shows forward end 48 of IR suppressor 20 in the final stages of alignment with aft end 24 of gas turbine engine 14.
- a resilient sealing gasket 74 makes a closed figure on aft end 24 facing a flange 76 on forward end 48.
- a lip 78 faces a groove 80.
- hook 46 is retracted and pulls against loop 42
- flange 76 is forced into engagement and compresses gasket 74 while lip 78 moves inside groove 80 to both stabilize the fit and further guard against the leakage of exhaust gases directly outward from the joint.
- the aft end of hook 46 is pivoted on a pivot 82 to a link 84.
- the opposed end of link 84 is pivoted by a pivot 86 to a support member 88 which is, in turn, rigidly affixed to a floor plate 90 of IR suppressor 20 by any convenient means such as by a bracket 92 affixed to floor plate 90 by any convenient means such as, for example, by bolts 94.
- Link 84 is rotatable by convenient camming action from the position shown in full line to the position shown in dashed line to rotate pivot 82 from its full line to its dashed line position.
- the latching action secured by one of the hook and loop attachment devices may be effective to continue holding IR suppressor 20 in place even if the other one is shot away.
Abstract
Description
Claims (12)
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US06/264,268 US4369937A (en) | 1981-05-18 | 1981-05-18 | Hinging and latching apparatus |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US06/264,268 US4369937A (en) | 1981-05-18 | 1981-05-18 | Hinging and latching apparatus |
Publications (1)
Publication Number | Publication Date |
---|---|
US4369937A true US4369937A (en) | 1983-01-25 |
Family
ID=23005289
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US06/264,268 Expired - Fee Related US4369937A (en) | 1981-05-18 | 1981-05-18 | Hinging and latching apparatus |
Country Status (1)
Country | Link |
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US (1) | US4369937A (en) |
Cited By (11)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2565293A1 (en) * | 1984-06-04 | 1985-12-06 | Aerospatiale | JET DILUATOR-DEVIATOR ASSEMBLY FOR AERODYNE TURBOMOTEUR |
US5622404A (en) * | 1993-10-26 | 1997-04-22 | Premier Marine, Inc. | Combination seat and storage system |
WO1999054204A1 (en) * | 1998-04-22 | 1999-10-28 | Pratt & Whitney Canada Corp | Jet engine exhaust nozzle |
US6253540B1 (en) * | 1982-07-08 | 2001-07-03 | General Electric Company | Removable baffle infrared suppressor |
US6267327B1 (en) * | 1999-04-02 | 2001-07-31 | Allison Advanced Development Company | Coupling system for connecting a gas turbine engine to an aircraft mounted exhaust system |
EP1582730A1 (en) | 2004-03-30 | 2005-10-05 | General Electric Company | Apparatus for exhausting gases from gas turbine engines |
US20050268595A1 (en) * | 2004-06-08 | 2005-12-08 | General Electric Company | Method and apparatus for suppressing infrared signatures |
US20060232077A1 (en) * | 2005-04-14 | 2006-10-19 | Courter Harry I | Lock release for motorized oven lock |
US20080267694A1 (en) * | 2007-04-30 | 2008-10-30 | Honeywell International, Inc. | Dual action structural latch |
US20100064740A1 (en) * | 2006-11-28 | 2010-03-18 | Eurocopter Deutschland Gmbh | Door lock for doors of aircraft, especially of helicopters |
US20130087663A1 (en) * | 2011-04-28 | 2013-04-11 | Bell Helicopter Textron Inc. | Self-aligning inlet plenum system for rotorcraft |
Citations (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2695803A (en) * | 1951-12-12 | 1954-11-30 | Summers J Mills | Latch fastener |
US4002024A (en) * | 1974-12-02 | 1977-01-11 | General Electric Company | Infrared suppression system for a gas turbine engine |
US4049220A (en) * | 1975-09-12 | 1977-09-20 | Rolls-Royce Limited | Ejector sleeves for aircraft mounted gas turbine engines |
SU290678A1 (en) * | 1969-08-19 | 1980-01-15 | Предприятие | Aircraft engine hood |
-
1981
- 1981-05-18 US US06/264,268 patent/US4369937A/en not_active Expired - Fee Related
Patent Citations (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2695803A (en) * | 1951-12-12 | 1954-11-30 | Summers J Mills | Latch fastener |
SU290678A1 (en) * | 1969-08-19 | 1980-01-15 | Предприятие | Aircraft engine hood |
US4002024A (en) * | 1974-12-02 | 1977-01-11 | General Electric Company | Infrared suppression system for a gas turbine engine |
US4049220A (en) * | 1975-09-12 | 1977-09-20 | Rolls-Royce Limited | Ejector sleeves for aircraft mounted gas turbine engines |
Cited By (19)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US6253540B1 (en) * | 1982-07-08 | 2001-07-03 | General Electric Company | Removable baffle infrared suppressor |
FR2565293A1 (en) * | 1984-06-04 | 1985-12-06 | Aerospatiale | JET DILUATOR-DEVIATOR ASSEMBLY FOR AERODYNE TURBOMOTEUR |
EP0165167A1 (en) * | 1984-06-04 | 1985-12-18 | AEROSPATIALE Société Nationale Industrielle | Jet dilution and deviation device to suppress the infrared radiation of a turbo motor |
US4662174A (en) * | 1984-06-04 | 1987-05-05 | Societe Nationale Industrielle Et Aerospatiale | Plume diluter diverter assembly for a turbine engine of a heavier than air machine |
US5622404A (en) * | 1993-10-26 | 1997-04-22 | Premier Marine, Inc. | Combination seat and storage system |
WO1999054204A1 (en) * | 1998-04-22 | 1999-10-28 | Pratt & Whitney Canada Corp | Jet engine exhaust nozzle |
US6109562A (en) * | 1998-04-22 | 2000-08-29 | Pratt & Whitney Canada Corp. | Aircraft construction |
US6267327B1 (en) * | 1999-04-02 | 2001-07-31 | Allison Advanced Development Company | Coupling system for connecting a gas turbine engine to an aircraft mounted exhaust system |
EP1582730A1 (en) | 2004-03-30 | 2005-10-05 | General Electric Company | Apparatus for exhausting gases from gas turbine engines |
JP2005280697A (en) * | 2004-03-30 | 2005-10-13 | General Electric Co <Ge> | Method and device for exhausting gas from gas turbine engine |
US20050268595A1 (en) * | 2004-06-08 | 2005-12-08 | General Electric Company | Method and apparatus for suppressing infrared signatures |
US6988674B2 (en) | 2004-06-08 | 2006-01-24 | General Electric Company | Method and apparatus for suppressing infrared signatures |
US20060232077A1 (en) * | 2005-04-14 | 2006-10-19 | Courter Harry I | Lock release for motorized oven lock |
US20100064740A1 (en) * | 2006-11-28 | 2010-03-18 | Eurocopter Deutschland Gmbh | Door lock for doors of aircraft, especially of helicopters |
US8360483B2 (en) * | 2006-11-28 | 2013-01-29 | Eurocopter Deutschland Gmbh | Door lock for doors of aircraft, especially of helicopters |
US20080267694A1 (en) * | 2007-04-30 | 2008-10-30 | Honeywell International, Inc. | Dual action structural latch |
US7448656B1 (en) * | 2007-04-30 | 2008-11-11 | Honeywell International Inc. | Dual action structural latch |
US20130087663A1 (en) * | 2011-04-28 | 2013-04-11 | Bell Helicopter Textron Inc. | Self-aligning inlet plenum system for rotorcraft |
US8998130B2 (en) * | 2011-04-28 | 2015-04-07 | Textron Innovations Inc. | Self-aligning inlet plenum system for rotorcraft |
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Legal Events
Date | Code | Title | Description |
---|---|---|---|
AS | Assignment |
Owner name: GENERAL ELECTRIC COMPANY Free format text: ASSIGNMENT OF ASSIGNORS INTEREST.;ASSIGNORS:BARR, SAMUEL R., JR. LEGAL REPRESENTATIVE OF SAMUEL R. BARR SR. DEC'D.;LE BELL, CLARENCE E.;REEL/FRAME:004065/0241;SIGNING DATES FROM 19811021 TO 19811023 Owner name: GENERAL ELECTRIC COMPANY, STATELESS Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNORS:BARR, SAMUEL R., JR. LEGAL REPRESENTATIVE OF SAMUEL R. BARR SR. DEC'D.;LE BELL, CLARENCE E.;SIGNING DATES FROM 19811021 TO 19811023;REEL/FRAME:004065/0241 Owner name: UNITED STATES OF AMERICA AS REPRESENTED BY THE SEC Free format text: ASSIGNMENT OF ASSIGNORS INTEREST. SUBJECT TO LICENSE RECITED.;ASSIGNOR:GENERAL ELECTRIC COMPANY;REEL/FRAME:004065/0243 Effective date: 19811019 Owner name: UNITED STATES OF AMERICA AS REPRESENTED BY THE SEC Free format text: ASSIGNMENT OF ASSIGNORS INTEREST. SUBJECT TO LICENSE RECITED;ASSIGNOR:GENERAL ELECTRIC COMPANY;REEL/FRAME:004065/0243 Effective date: 19811019 |
|
FEPP | Fee payment procedure |
Free format text: MAINTENANCE FEE REMINDER MAILED (ORIGINAL EVENT CODE: REM.); ENTITY STATUS OF PATENT OWNER: LARGE ENTITY |
|
LAPS | Lapse for failure to pay maintenance fees | ||
STCH | Information on status: patent discontinuation |
Free format text: PATENT EXPIRED DUE TO NONPAYMENT OF MAINTENANCE FEES UNDER 37 CFR 1.362 |
|
FP | Lapsed due to failure to pay maintenance fee |
Effective date: 19870125 |